Similarly shaped airfoils to NACA63-316 a=0.5
New! Bulk download of polars in Excel format: NACA63-316%20a%3D0.5.xlsx
Info | DAT and DXF files | Shape | Venkataraman Fit | Applications (0) | Similarly shaped airfoils
Plain Flapped Shapes: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Basic Data: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl | Curve fits | Lift curve slopes
Data source comparison (Codes, CFD, Wind tunnel)
Compressibility Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Roughness Effects: cl vs α | cd vs α | cm vs α | cl/cd vs α | cd vs cl | cl/cd vs cl | cl vs cd | cm vs cl
Plain Flap Effects: cl,max vs flap deflection: all flap chords | 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cl vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cm vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Plain Flap Effects: cd vs α for various flap deflections: 25% flap chord | 30% flap chord | 35% flap chord | 40% flap chord
Disclaimer: All information presented herein is delivered without guarantee or warranty of any kind. The user assumes the entire risk of use of this information.
2. GA 35-216
3. NACA64-316 a=0.5
4. NACA64-316 a=0.6
5. GA 37-216
6. NACA63-316 a=0.8
7. NACA63-416 a=0.0
8. NACA63-316 a=0.2
9. NACA64-316 a=0.8
10. NACA63-416
11. NACA64-416 a=0.0
12. NACA63-416 a=0.2
13. NACA64-316 a=0.2
14. NACA63-317 a=0.5
15. NACA63-315 a=0.5
16. NACA64-416
17. NACA63-317 a=0.6
18. NACA64-416 a=0.2
19. NACA63-315 a=0.6
20. NACA63-316
21. GA 35-215